www.specialmetals.com INCONEL nickel-iron-chromium alloy 76 (UNS N976) is a precipitation-hardenable alloy that provides high mechanical strength in combination with good fabricability. The characteristics of the alloy are similar to those of INCONEL alloy 718 except that alloy 76 is more readily fabricated, particularly by machining. (The properties of alloy 718 are described in the publication INCONEL alloy 718, on the website www.specialmetals.com.) The limiting chemical composition of INCONEL alloy 76 is listed in Table 1. The substantial nickel and chromium contents provide good resistance to oxidation and corrosion. The primary precipitation-hardening constituents of the alloy are niobium and titanium. The aluminum content also contributes to the hardening response. The precipitation-hardening system in INCONEL alloy 76 provides the desirable characteristic of delayed hardening response during exposure to precipitation temperatures. That characteristic gives the alloy excellent resistance to postweld strain-age cracking. INCONEL alloy 76 is used for a variety of applications that require high strength combined with ease of fabrication. In the aerospace field, the alloy is used for turbine discs, shafts, and cases; diffuser cases; compressor discs and shafts; engine mounts; and fasteners. In addition to aerospace applications, the alloy is used for turbine discs in large industrial gas turbines. Property values in this publication are given in both United States customary units and the International System of Units (SI). The SI unit of stress is the pascal (Pa), which is equivalent to newton per square meter. The approximate relationship between the pascal and the pound per square inch (psi) is 1 Pa =.145 psi, or 1 psi = 6,895 Pa. Table 1 - Limiting Chemical Composition,, of INCONEL alloy 76 Nickel (Plus Cobalt)...39.-44. Chromium...14.5-17.5 Iron...Balance b Niobium (plus Tantalum)...2.5-3.3 Titanium...1.5-2. Aluminum...4 max. Carbon...6 max. Copper...3 max. Manganese...35 max. Silicon...35 max. Sulfur...15 max. Phosphorus...2 max. Boron...6 max. Cobalt a...1. max. Physical Constants and Thermal Properties Some physical constants for INCONEL alloy 76 are listed in Table 2. Thermal and electrical properties are reported in Table 3. Values shown for thermal conductivity were calculated from measurements of electrical resistivity. Specific-heat values were calculated from chemical composition. All values given for thermal and electrical properties were determined for precipitation-hardened material. Modulus of elasticity and Poisson s ratio for precipitation-hardened material at various temperatures are shown in Table 4. The modulus data were determined by the dynamic method. Poisson s ratio was calculated from moduli of elasticity. INCONEL alloy 76 undergoes a small amount of contraction during precipitation hardening. The amount of contraction is typically.9. Table 2 - Physical Constants Density Annealed, lb/in 3...291 Mg/m 3...8.5 Precipitation-Hardened, lb/in 3...292 Mg/m 3...8.8 Melting Range, F...2434-2499 C...1334-1371 Specific, 7 F, Btu/lb F...16 21 C, J/kg C...444 Permeability at oersted (15.9 ka/m) Annealed 74 F (23 C)...1.11-19 F (-78 C)...1.2-32 F (-196 C)...Magnetic Precipitation-Hardened 74 F (23 C)...1.1-19 F (-78 C)...1.4-32 F (-196 C)...Magnetic Curie, F...<-19 C...<-78 INCONEL alloy 76 a Determination not required for routine acceptance. b Reference to the balance of a composition does not guarantee this is exclusively of the element mentioned but that it predominates and others are present only in minimal quantities.
INCONEL alloy 76 Table 3 - Thermal Properties Electrical Thermal Coefficient of Specific Resistivity Conductivity a Expansion b c F ohm Btu in/ft 2 circ mil/ft hr F 1-6 in/in/ F Btu/lb F -32 527 55 - - 7 592 87 -.16 61 96 7.4.11 3 622 13 7.83.113 635 11 8.7.117 5 647 117 8.25.12 659 124 8.42.124 7 671 13 8.5.127 683 136 8.57.131 9 695 141 8.64.134 77 147 8.73.138 1 717 152 8.84.141 1 - - 8.97.145 13 - - 9.11.148 C µω m W/m C µm/m/ C J/kg C -196.876 7.9 - - 2.985 12.5-444 1.15 14. 13.46 461 15 1.35 14.8 14.11 473 1.55 15.9 14.53 49 25 1.75 16.7 14.85 52 3 1.9 17.6 15.8 515 35 1.11 18.5 15.25 528 1.13 19.2 15.39 536 45 1.145 19.9 15.5 553 5 1.16 2.6 15.59 565 55 1.1 21.3 15.79 582 1.195 22.1 15.97 595 65 - - 16.2 67 7 - - 16.42 62 Table 4 - Modulus of Elasticity a Tensile Modulus Shear Modulus F 1 3 1 3 C GPa GPa Poisson s Ratio b -32 31.6 11.6.362 7 3.4 11..382 29.9 1.8.387 29. 1.4.393 27.9 1..395 27. 9.6.45 25.9 9.3.395 1 24.7 8.8.43 13 24. 8.5.417 Poisson s Ratio b -196 218.362 2 21 76.382 26 74.389 72.389 3 194 7.392 188 67.45 5 181 65.44 174 63.395 7 166 59.415 a Determined by dynamic method on precipitation-hardened material. b Calculated from moduli of elasticity. a Calculated from electrical resistivity. b Average coefficient between 78 F (26 C) and temperature shown. c Calculated from chemical composition. 2
INCONEL alloy 76 Mechanical Properties The high-strength of precipitation-hardened INCONEL alloy 76 is maintained at temperatures up to 13 F (75 C). Optimum mechanical properties for the intended service temperature are achieved by the use of one of two heat treatments. HEAT TREATMENTS The heat treatments used for alloy 76 are designed to produce either high tensile properties for room- and moderate-temperature applications or high stress-rupture properties for applications up to 13 F (75 C). For optimum creep and rupture properties, the alloy receives a three-part heat treatment: A Solution - 17-185 F (925-11 C) for a time commensurate with section size, air cool. Stabilizing - 155 F (845 C)/3 hr, air cool. Precipitation - 1325 F (72 C)/8 hr, furnace cool at F (55 C)/hr to 115 F (62 C)/8 hr, air cool. For tensile-limited applications, a two-part treatment is used: B Solution - 17-185 F (925-11 C) for a time commensurate with section size, air cool. Precipitation - 135 F (73 C)/8 hr, furnace cool at F (55 C)/hr to 115 F (62 C)/8 hr, air cool. The heat treatments described above are based on metal temperatures and are derived from batch rather than continuous furnace operations. The solution-treatment procedures may not be applicable to continuous operations since continuous heat treating is normally performed by short-time exposure in the hot zone of a furnace set at higher temperatures. TENSILE PROPERTIES Room-temperature tensile properties of cold-rolled sheet in the solution-treated and precipitation-hardened conditions are given in Table 5. All specimens were from the transverse direction. Typical room-temperature tensile properties of hotfinished material given s A and B are listed in Table 6. The data illustrate the improvement in tensile properties, particularly yield strength, provided by B. All of the tests were performed on longitudinal specimens. Tensile properties of forged discs at room temperature and 1 F are listed in Table 7. Data showing the effects of forging temperature on mechanical properties are given in the section on hot forming. Table 5 - Room- Tensile Properties of Cold-Rolled Sheet Thickness in mm Tensile Strength (.2 Offset).4 1.2 Solution 19.8 757 55.5 383 47 Treated.4 1.2 A 186. 1282 148.5 124 22.4 1.2 B 193.5 1334 161.3 1112 24.62 1.57 A 189. 133 153.5 158 18.62 1.57 B 191. 1317 159. 196 2 Form in Size Table 6 - Typical Room- Tensile Properties of Hot-Finished Material mm (.2 Offset) Reduction of Area, Rod.562 Dia. 14.3 A 186. 1282 144. 993 19 28 Rod 8. Dia 23 A 189. 133 146. 7 18 28 Flat 1.25 Thick 31.8 B 193.5 1334 161.5 1114 2 38 Rod.562 Dia. 14.3 B 193. 1331 158. 189 21 55 F C Table 7 - Tensile Properties of Forged Discs (.2 Offset) Reduction of Area, 7 2 Solution 18. 745 41.7 288 5 55 Treated 7 2 A 1.5 1245 142. 979 17 19 1 65 A 143.5 989 119.5 824 21 27 7 2 B 183. 1262 157.4 185 22 43 3
INCONEL alloy 76 Table 8 shows the effects of temperatures from -32 F (-196 C) to 9 F (4 C) on the tensile properties of precipitation-hardened hot-finished rod. The tests were performed on longitudinal specimens from.562-in. (14.3- mm) rod heat-treated as indicated. INCONEL alloy 76 retains substantial strength at elevated temperatures. Figures 1 and 2 show tensile properties to 1 F (76 C) of cold-rolled sheet given s A and B. The specimens were from.4-in. (1.2-mm) sheet and were tested in the transverse direction. F C Table 8 - Tensile Properties of Precipitation-Hardened Hot-Finished Rod a (.2 Offset) Reduction of Area, -32-196 A 232.5 163 169. 1165 24 29 B 236.5 1631 174. 1 28 54-65 -54 A 27.5 1431 163. 1124 18 29 B 28.5 1438 161. 111 22 52 7 2 A 192. 1324 155.5 172 16 32 B 193. 1331 158. 189 21 55 9 4 A 168. 1158 134.5 927 15 38 B 165.5 1141 135.5 934 2 52 a.562-in. (14.3-mm) diameter., C, C 1 3 5 7 13 1 1 3 5 7 13 1 16 1 16 1 Stress, 14 12 6 (.2 Offset) 9 7 5 Stress, Stress, 14 12 6 (.2 Offset) 9 7 5 Stress, 4 2 Elongation 3 4 2 Elongation 3 1 1 1 1, F, F Figure 1. High-temperature tensile properties of cold-rolled sheet given A. Figure 2. High-temperature tensile properties of cold-rolled sheet given B. 4 Form Table 9 - Room- Compressive and Tensile Properties Compressive (.2 Offset) Tensile (.2 Offset) Hot-Rolled Rod A 159.9 112 148. 12 189. 133 19 B 16.4 116 153.4 158 19.2 1311 26 Hot-Rolled Plate A 16.4 116 148. 12 19.5 1313 19 B 156.6 1 155.4 171 192. 1324 22
INCONEL alloy 76 The strength of alloy 76 in compression is somewhat higher than its strength in tension. Table 9 is a comparison of compressive yield strength and tensile properties. SHEAR AND BEARING STRENGTH The shear strength of INCONEL alloy 76 in various forms and conditions is shown in Table 1. The values are from guillotine shear tests in which the specimens were loaded in double shear. Tensile properties of the specimens are included for comparison. Alloy 76 sheet has high bearing properties. Table 11 gives bearing yield strength and ultimate strength of specimens from precipitation-hardened cold-rolled sheet. The data are from pin-type bearing tests. The specimen was subjected to tensile stress while supported by a.25-in. (6.35-mm) diameter pin inserted with a tight fit through a hole whose center was.375-in. (9.52-mm) from the edge of the specimen (edge distance ratio of 1.5). Form Table 1 - Room- Shear Strength and Tensile Properties Shear Strength (.2 Offset) Hot-Rolled Rod A 127. 876 189. 133 148. 12 19. B 13.4 899 19.2 1311 153.4 158 26. Hot-Rolled Plate A 115. 793 19.5 1313 148. 12 19. B 122.3 843 192. 1324 155.4 171 22. Cold-Rolled Sheet A 115. 793 189. 133 147.5 117 15.5 B 119.7 825 196.5 1355 163.5 1127 19.5 Sheet Thickness in. mm Specimen Orientation Table 11 - Bearing Strength a of Strength Bearing (.2 Offset) Bearing Strength Tensile (.2 Offset).62 1.57 A Transverse 22.1 1518 299.8 267 142.9 985 179.2 1236 B Longitudinal 232.3 162 316.3 2181 162.3 1119 21.1 1387 B Transverse 234.7 1618 318.7 2197 161.1 1111 192.1 1324.89 2.26 A Transverse 24.3 149 279.7 1928 147.5 117 189. 133 B Longitudinal 234.3 1615 34.9 212 159.5 1 198.5 1369 B Transverse 229.6 1583 38.3 2126 163.5 1127 196.5 1355 a Pin diameter of.25 in. (6.35 mm). Edge distance ratio of 1.5. FATIGUE STRENGTH AND FRACTURE TOUGHNESS 95 65 The rotating-beam fatigue strength at room temperature and 1 F (65 C) of alloy 76 in the two precipitationhardened conditions is shown in Figures 3 and 4. As 85 illustrated by the curves, B produces higher fatigue strength. Longitudinal specimens from.562-in. 75 (14.3-mm) diameter rod were used for the tests. The 7 specimens were polished with 5-grit paper before being tested. The material given A (Figure 3) had 65 a grain size of ASTM 7.5 and the following roomtemperature tensile properties: 6, 186 (1282 ) 55 (.2 Offset), 144 (993 ) 5 19 1 5 Stress, 9 1 F (65 C) Room 1 6 Cycles to Failure 1 7 55 5 45 35 1 8 Stress, Figure 3. Rotating-beam fatigue strength of hot-rolled rod given A. 5
INCONEL alloy 76 The material given B (Figure 4) had a grain size of ASTM 6 and room-temperature tensile properties of:, 21 (1386 ) (.2 Offset), 157.5 (186 ) 26 Low-cycle fatigue properties of INCONEL alloy 76 given B are shown in Figure 5. The tests were performed on transverse specimens from.25-in. (6.4-mm) plate. The specimens were polished with 5-grit paper. The grain size of the plate was ASTM 4, and room-temperature tensile properties were:, 1 (1241 ) (.2 Offset), 143.5 (989 ) 22 Plane-strain fracture-toughness tests performed on five specimens from an 8.5-in. (216-mm) diameter hot-finished round produced an average K IC value of 86.5 in. (95.8 m). The tests were performed by the slow-bend method on precipitation-hardened ( A) material. Longitudinal specimens were used. Stress, 95 9 85 75 7 65 6 55 Room and 1 F (65 C) 5 35 1 5 1 6 1 7 1 8 Cycles to Failure Figure 4. Rotating-beam fatigue strength of hot-rolled rod given B. Total Strain Range, in./in..1.1 1 F (65 C) Room and F (54 C) 65 55 5 45 Stress, IMPACT STRENGTH Precipitation-hardened INCONEL alloy 76 is metallurgically stable and is not embrittled by long-time exposure to high temperatures. Table 12 gives the results of room-temperature Charpy V-notch tests on hot-finished rod in the as-heat-treated condition and after exposure to F (54 C) and 1 F (65 C) for up to hr. As indicated by the values, B produces higher impact strength than does A. Charpy V-notch tests at -32 F (-196 C) yielded impact strengths of 16 ft lb (22 J) for material given A and 59 ft lb ( J) for material given B. The tests were performed on specimens from.562-in. (14.3-mm) diameter rod. Table 12 - Effect of High- Exposure on Room- Impact Strength Exposure Exposure Charpy V-Notch Time, Impact Strength F C hr ft lb J 7 2 - A 23 31 54 A 23 31 5 A 21 28 A 26 35 1 65 A 28 38 5 A 23 31 A 29 39 7 2 - B 61 83 54 B 63 85 5 B 58 79 B 63 85 1 65 B 59 5 B 54 73 B 54 73 CREEP AND RUPTURE PROPERTIES Because of its high creep-rupture strength, INCONEL alloy 76 is widely use for applications such as gas-turbine components that involve extended exposure to elevated temperatures. For creep- or rupture-limited applications, the alloy should be given the triple heat treatment ( A)..1 1 2 1 4 1 3 Cycles to Failure 1 5 1 6 Figure 5. Low-cycle fatigue strength of hot-rolled plate given B. 6
INCONEL alloy 76 INCONEL alloy 76 is notch-ductile under stressrupture conditions. The Larson-Miller parameter plot of Figure 6 compares rupture-strength curves for smooth-bar and notched-bar specimens. The notched specimens had a stress-concentration factor (K t ) of 4.. The creep strength of alloy 76 at temperatures of 1 F to 1 F (595 C to 76 C) is shown in Figure 7. Rupture strength of the alloy over the same temperature range is shown in Figure 8. The creep and rupture properties of alloy 76 are further illustrated by Figures 9 and 1, which shown stresses to produced rupture and selected amounts of plastic strain in hr and hr. The results of relaxation tests performed at three different temperatures with an initial stress of 6 (414 ) are given in Table 13. The alloy showed no loss of strength and good ductility after completion of the tests. A specimen relaxation-tested for 13,377 hr at 1 F (595 C) and an initial stress of 6 (414 ) had the following room-temperature tensile properties:, 19 (131 ) (.2 Offset), 15.5 (138 ) 11.5 Reduction of Area, 33.5 All creep and rupture data reported here are for material given A. Rupture Life, hr Stress, 6 4 2 1 1, 32, F 5 7 Smooth Bar Notch Bar (K t = 4.) 1 1 13 1, F 34 36 38 4 42 44 46 48 5 52 54 P = (46 + T) (23.656 + log t) x 1-3 Stress, Figure 6. Larson-Miller parameter plot of rupture strength of precipitation-hardened ( A) INCONEL alloy 76. In the parameter, T is temperature in F and t is time in hours. Stress, 1 F (65 C) 13 F (75 C) 1 F (595 C) 1 F (76 C) Stress, 1.1.1.1 Creep Rate, /hr.1.1 1. Figure 7. Typical creep strength of precipitation-hardened ( A) material. 7
INCONEL alloy 76 Stress, 1 F (595 C) 1 F (65 C) 13 F (75 C) Stress, 1 1 1 Rupture Life, hr 1 F (76 C) 1,, Figure 8. Typical rupture strength of precipitation-hardened ( A) material. 14 55, C 65 7 75 14 55, C 65 7 75 13 9 13 9 12 Rupture 12 11 1. Plastic Strain 7 11 Rupture 7 Stress. 9 7 6.5 Plastic Strain.2 Plastic Strain 5 Stress. Stress. 9 7 6.5 Plastic Strain 1. Plastic Strain 5 Stress. 5 4 3 5 4.2 Plastic Strain 3 3 3 2 1 1 13, F 1 15 2 1 1 13, F 1 15 Figure 9. Typical -hr creep-rupture properties of precipitationhardened ( A) INCONEL alloy 76. Figure 1. Typical -hr creep-rupture properties of precipitation-hardened ( A) INCONEL alloy 76. Table 13 - Relaxation of Precipitation-Hardened ( A) Material Stress to Maintain Constant Strain hr 1 hr hr hr 1, hr F C 54 6. 414 6.5 417 61. 421 61.8 426 62. a 427 1 595 6. 414 65. 448 63.5 438 62. 427 62. 427 1 65 6. 414 57. 393 57. 393 56. 386 - - a Extrapolated. Test discontinued at 6 hr. 8
INCONEL alloy 76 Microstructure INCONEL alloy 76 is a precipitation-hardenable alloy with a face-centered-cubic crystal structure. The alloy is strengthened by the precipitation of a gamma prime or gamma double-prime phase during heat treatment in the 1-1 F (595-76 C) temperature range. A produces both the gamma prime, which has a face-centered-cubic structure, and the gamma double prime, which has a body-centered-tetragonal structure. B normally produces only the gamma prime phase. The phases have a Ni 3 (Nb, Ti, Al) composition. They are not visible at magnifications achieved by optical microscopy; electron microscopy is required for resolution. Overaging or extended service at precipitation-hardening temperatures results in a transformation of the phases to a needle-shaped, orthorhombic Ni 3 Nb structure. That structure may be visible with optical microscopy. Corrosion Resistance The composition of INCONEL alloy 76 enables it to resist corrosion in various environments. The alloy s chromium content provides resistance to oxidizing media, and its nickel content provides resistance to reducing environments. Table 14 lists corrosion rates for the alloy in several acid solutions at boiling temperatures. Other tests have shown the alloy to have poor resistance to boiling 5 sulfuric acid and to boiling 38 and concentrated hydrochloric acid. The nickel content of alloy 76 gives it resistance to both chloride-ion and hydroxyl-ion stress-corrosion cracking. Stressed specimens did not crack in 3 days of exposure to boiling 42 magnesium chloride. A test in boiling 5 sodium hydroxide resulted in a cracking time of 5 days. HEATING AND PICKLING INCONEL alloy 76, like other high-nickel alloys, must be clean before it is heated and must be heated in a low-sulfur atmosphere. To prevent possible contamination of the metal, all foreign substances such as grease, oil, paint, and shop soil must be removed prior to a heating operation. Fuels for open heating must be low in sulfur, and the furnace atmosphere should be slightly reducing to prevent excessive oxidation of the material. Annealing procedures for alloy 76 depend on the section size of the workpiece and the amount of cold work to which it has been subjected. Figure 11 shows the effects of various annealing temperatures on the tensile properties of cold-rolled.6-in. (1.5-mm) sheet with 37.5 cold reduction. The material was held at temperature for 5 min and air-cooled. Procedures for solution treatment and precipitation hardening are discussed in the section on mechanical properties The aluminum, titanium, and chromium in INCONEL alloy 76 produce refractory oxides during most heating operations, and the alloy normally must be pickled if a bright surface is required. Stress, 16 14 12 9 91 Annealing, C 92 93 94 95 96 1 9 Table 14 - Corrosion Rates in Boiling Acid Solutions 7 Corrosion Rate Solution Material Condition mpy a mm/a 1 H 2 SO 4 Annealed 123 3.12 4 H 3 PO 4 Annealed 55 1.4 7 HNO 3 Annealed 14.356 7 HNO 3 Age Hardened 6.6 1.54 25 HNO 3 Age Hardened 1.7.43 a Mils penetration per year. Working Instructions INCONEL alloy 76 has good working characteristics and is readily fabricated by conventional procedures for highstrength alloys. Of particular significance are the machinability and weldability of the alloy. Hardness, Ra 6 4 2 As Rolled (.2 Offset) Hardness Elongation 165 1675 17 1725 175 1775 Annealing, F Figure 11. Effect of annealing temperature on mechanical properties of cold-rolled sheet. Specimens were held at temperature for 5 min and air-cooled before being tested. 5 3 Stress, 9
INCONEL alloy 76 HOT AND COLD FORMING INCONEL alloy 76 has excellent hot formability at temperatures from 1 F (87 C) to 2 F (115 C). Test results indicate, however, that optimum mechanical properties are obtained with hot-working temperatures in the 1 F (9 C) to 2 F (115 C) range. Tables 15 and 16 show the effects of forging temperature on mechanical properties at room temperature and 1 F (65 C). The specimens were from 6-in. (15-mm) hot-rolled squares that had been upset-forged from 4-in. (-mm) to 1.375-in. (35- mm) thick. The forgings were given A before being tested. Forging at temperatures in the lower portion of the hotworking range to develop high mechanical properties, a procedure often required with similar alloys, is not necessary for INCONEL alloy 76. The higher finishforging temperature increases die life and enables parts to be forged closer to the finished size. Cold forming of alloy 76 is performed by standard methods for high-nickel alloys. The work-hardening rate of the alloy is shown in Figure 12. The cold-forming characteristics of alloy 76 are similar to those of INCONEL alloy 718. Alloy 76, however, is somewhat softer in the annealed condition and requires lower forces for deformation. Additional information on fabricating is available in the Special Metals publication Fabricating on the website, www.specialmetals.com. F Table 15 - Effect of Forging on Room- Properties of Precipitation-Hardened a Material C Tensile Strength (.2 Offset) Reduction of Area, Hardness, Rc 1 9 175. 127 134. 924 14 19 36 6.5 19 14 178. 1227 14. 965 16 18 35 7.5 195 177.5 1224 142.5 983 17 16 38 7. 2 115 176. 1213 14.5 969 16 19 36 6.5 a All material received A after being forged. ASTM Grain Size Forging F Table 16 - Effect of Forging on High- Properties of Precipitation-Hardened a Material C Tensile Properties at 1 F (65 C) (.2 Offset) Reduction of Area, Rupture Properties at 1 F (65 C) and 15 (724 ) Rupture Life, hr Reduction of Area, 1 9 142. 979 123. 848 23 48 28.1 22 38 19 14 143.5 989 124. 855 21 46 24.4 25 43 195 144. 993 125. 862 23 54 62.2 22 29 2 115 146. 7 123. 848 2 43 39.2 14 31 a All material received A after being forged. 1
INCONEL alloy 76 Diamond Pyramid (Vickers) Hardness Number 45 35 3 25 15 5 INCONEL alloy 718 1 2 3 4 5 6 Cold Reduction, MACHINING MONEL alloy Copper Aluminum Type 34 Stainless INCONEL alloy 625 INCONEL alloy 76 INCONEL alloy Nickel Mild Steel Figure 12. Effect of cold work on hardness of INCONEL alloy 76 and other materials. Good machinability is one of the outstanding characteristics of INCONEL alloy 76. The superiority of alloy 76 over some other high-strength alloys is shown by the toollife/cutting-velocity comparison in Figure 13. Additional information on machining is available in the Special Metals publication Machining on the website, www.specialmetals.com. Cutting Speed, surface ft/min 9 7 5 3 9 7 6 5 4 3 1 INCONEL alloy INCONEL alloy 76 INCOLOY alloy 91 INCONEL alloy 718 1 Tool Life, min 6 4 2 1 Figure 13. Machinability of annealed material. Specimens were machined with carbide tools and with water-soluble oil as coolant. 7 Cutting Speed, surface m/min JOINING INCONEL alloy 76 has excellent weldability. The alloy s niobium/titanium precipitation-hardening system provides a delayed response to precipitation-hardening temperatures. The sluggish aging response imparts a high degree of resistance to post-weld strain-age cracking. The alloy also resists underbead cracking (microfissuring). Most joints that are not highly restrained can be repair-welded and directly re-aged with no cracking. Pierce-Miller patch tests performed on four thicknesses of annealed sheet showed no cracking after specimens were welded, age-hardened, repairwelded, and re-aged. Repair welds in highly restrained joints, however, may require solution treatment before being re-aged. Welding procedures for alloy 76 are the same as for INCONEL alloy 718. Gas-tungsten-arc welding with INCONEL Filler Metal 718 is the recommended process. The alloy has also been joined by the flash-butt process; sound welds were produced with less upset pressure than that needed for alloy 718. Precipitation-hardened welds in alloy 716 exhibit high strength levels. Table 17 gives tensile properties of transverse specimens from autogenous gas-tungsten-arc welds in.62-in. (1.57-mm) sheet. Tensile properties of joints welded with the gas-tungsten-arc process and INCONEL Filler Metal 718 are listed in Table 18. The values are for transverse specimens from butt joints in.5-in. (13-mm) thick flats. Additional information on joining is available in the Special Metals publication Joining on the website, www.specialmetals.com. Table 17 - Transverse Tensile Properties of Autogenous Gas-Tungsten-Arc Welds a Test Tensile Strength (.2 Offset) F C 85 3 A 153. 155 133.5 92 85 3 B 16. 113 144. 993 54 A 14.5 969 114. 786 1 65 A 126. 869 113. 779 a Specimens were from joints in.62-in. (1.57-mm) sheet. All specimens fractured in weld metal. 11
www.specialmetals.com Table 18 - Transverse Tensile Properties of Gas-Tungsten-Arc Welds Made with INCONEL Filler Metal 718 a Test Tensile Strength (.2 Offset) F C 85 3 A 176. 1213 14.5 969 85 3 B 176.5 1217 144. 993 54 A 151.5 145 123.5 852 54 B 151. 141 122.5 845 1 65 A 144.5 996 12.5 831 a Specimens were from butt joints in.5-in. (13-mm) thick flat. All specimens fractured in weld metal. Available products and specifications INCONEL alloy 76 is designated as UNS N976. Alloy 76 is available as round bar and forging stock. Rod, Bar, Wire, Forgings, and Forging Stock - SAE AMS 571, AMS 572, AMS 573 (Bars, Forgings and Rings) Plate, Sheet, and Strip - SAE AMS 565 and AMS 566 (Sheet, Strip and Plate), Publication Number SMC-91 Copyright Special Metals Corporation, 4 (Sept 4) INCOLOY, INCONEL, and MONEL are trademarks of the Special Metals Corporation group of companies. The data contained in this publication is for informational purposes only and may be revised at any time without prior notice. The data is believed to be accurate and reliable, but Special Metals makes no representation or warranty of any kind (express or implied) and assumes no liability with respect to the accuracy or completeness of the information contained herein. Although the data is believed to be representative of the product, the actual characteristics or performance of the product may vary from what is shown in this publication. Nothing contained in this publication should be construed as guaranteeing the product for a particular use or application. U.S.A. Special Metals Corporation 3 Riverside Drive Huntington, WV 2575-1771 Phone +1 (34) 526-5 +1 () 334-4626 Fax +1 (34) 526-5643 4317 Middle Settlement Road New Hartford, NY 13413-5392 Phone +1 (315) 798-29 +1 () 334-8351 Fax +1 (315)798-216 United Kingdom Special Metals Wiggin Ltd. Holmer Road Hereford HR4 9SL England Phone +44 () 1432 382 Fax +44 () 1432 2643